Vanes Patents (Class 415/191)
  • Patent number: 11028822
    Abstract: A wind turbine comprises a nacelle, a drive shaft extending from the nacelle along a shaft axis, a plurality of turbine blades coupled to the drive shaft and extending radially relative to the shaft axis, and a first static airfoil structure coupled to the wind turbine to influence airflow exiting the plurality of turbine blades. A method of increasing wind turbine efficiency in a wind farm comprises positioning a first wind turbine having a first plurality of turbine blades at least partially upstream of a second wind turbine having a second plurality of turbine blades, producing a wake field of exit air behind the first plurality of turbine blades, directing air outside of the wake field into the wake field to increase speed of airflow in the wake field, and directing the airflow into the second plurality of turbine blades of the second wind turbine.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: June 8, 2021
    Assignee: University of Massachusetts
    Inventors: Shujaut Bader, Blair Perot
  • Patent number: 11022087
    Abstract: The double-regulated turbine comprises a spherical hub, adapted to rotate around a first rotation axis, and blades, which are each able to be swivelled relative to the hub around a second rotation axis, transversal to the first rotation axis, by respective coupling flanges that are mounted fixedly on the spherical hub and that include each an attachment surface for a corresponding blade. The attachment surface of the coupling flanges includes a flat portion.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: June 1, 2021
    Assignee: Alstom Renewable Technologies
    Inventor: Hai Trieu Phan
  • Patent number: 11002293
    Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 11, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Karan Anand, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac, Thomas Veitch
  • Patent number: 10968777
    Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Kyle J. Brevick
  • Patent number: 10934870
    Abstract: The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls Royce Corporation
    Inventors: Michael J. Whittle, Daniel K. Vetters, Jeffrey A. Walston, Eric Koenig
  • Patent number: 10837298
    Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately +/?0.049 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: November 17, 2020
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Mariano Medrano, Jr., Charles A. Ellis
  • Patent number: 10837316
    Abstract: A strut shield collar can include: a tubular portion including a tubular inside surface and a tubular outside surface; a flange portion extended from the tubular portion toward an outside of the tubular portion and including a flange inside surface; and a grid type mesh formed on at least one of the tubular inside surface and the flange inside surface, wherein the grid type mesh comprises a groove portion and a rib portion, and the groove portion is thinner than the rib portion.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: November 17, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Chad Garner
  • Patent number: 10823083
    Abstract: An epicyclic gearbox includes a sun gear assembly, a planet gear assembly, and a ring gear assembly engaged with a forward planet gear and an aft planet gear of the planet gear assembly. A first axial shroud is also provided positioned forward of the forward planet gear or aft of the aft planet gear along an axial direction. The first axial shroud covers substantially all of a forward side of the forward planet gear or an aft side of the aft planet gear. The planet gear assembly is coupled to a planet gear carrier, the planet gear carrier including a radial shroud including one or more radial shroud surfaces extending along at least a portion of an outer circumference of the forward planet gear and along at least a portion of an outer circumference of the aft planet gear.
    Type: Grant
    Filed: October 18, 2018
    Date of Patent: November 3, 2020
    Assignee: GE Avio S.r.l.
    Inventor: Michele Gravina
  • Patent number: 10823178
    Abstract: A radial compressor, with a rotor-side impeller, a stator-side housing, an inflow passage via which medium to be compressed can be fed to the impeller in the axial direction, a diffuser via which compressed medium can be conducted in the radial direction away from the impeller in the direction of a spiral housing section of the housing The diffuser radially outside in a transition region to the spiral housing section has an enlarging flow cross section.
    Type: Grant
    Filed: November 21, 2018
    Date of Patent: November 3, 2020
    Assignee: MAN Energy Solutions SE
    Inventors: Andreas Lesser, Hannes Benetschik, Christoph Heinz
  • Patent number: 10815811
    Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Ganesh Seshadri, Mahendran Manoharan
  • Patent number: 10808563
    Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
  • Patent number: 10774650
    Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
    Type: Grant
    Filed: October 12, 2017
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Thomas J. Praisner
  • Patent number: 10760425
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Veera Venkata Naga Krishna Satish Koyyalamudi, Matthew John McKeever, Kevin Michael Barnett
  • Patent number: 10751958
    Abstract: A composite woven outlet guide vane (32) and method of forming are depicted. The guide vane (32) is formed by use of a preform structure (100) with a core (150) which is removed following the manufacture.
    Type: Grant
    Filed: May 8, 2014
    Date of Patent: August 25, 2020
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Mark Ernest Vermilyea
  • Patent number: 10711615
    Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: July 14, 2020
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Wesley Smith, David Medrano, Charles A. Ellis
  • Patent number: 10704393
    Abstract: Disclosed is an airfoil array segment (110, 120, 130, 140, 150) of an airfoil array for a turbomachine, the airfoil array segment including a platform (10) having a platform surface, as well as at least two airfoils (20, 30). The platform surface has a depression (111, 121, 131, 141, 151) which extends up to the first airfoil and contacts the pressure side (21) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges (23, 33) and which contacts the pressure side (21) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges (23, 33). At least one lowest point (112, 122) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges (23, 33). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.
    Type: Grant
    Filed: May 9, 2018
    Date of Patent: July 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Fadi Maatouk, Markus Brettschneider, Inga Mahle
  • Patent number: 10689996
    Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: June 23, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Gilles Pierre-Marie Notarianni, Audrey Laguerre, Stephane Roger Mahias
  • Patent number: 10655502
    Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines at least one airfoil opening. At least one retention clip has an arcuate portion extending from a first elongated leg portion. The first elongated leg portion and the arcuate portion are received through the at least one airfoil opening such that the at least one retention clip limits movement of the airfoil relative to the first shroud.
    Type: Grant
    Filed: May 26, 2017
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian Barainca, Gary F. Fowler
  • Patent number: 10655483
    Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: May 19, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
  • Patent number: 10633989
    Abstract: A nozzle has an airfoil, and the nozzle is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between opposing walls to aerodynamically interact with a fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. A trailing edge of the airfoil deviates from an axial plane by about 0.1 degrees to about 5 degrees. A turbomachine comprising a plurality of nozzles is also provided.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Shashwat Swami Jaiswal, Rohit Chouhan, Lukasz Szajko
  • Patent number: 10619497
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: April 14, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Pascal Pierre Nicolas Routier, Jean-Armand Marc Emilien Destouches, Thomas Michel Julien Mervant, Ludovic Pintat, Guillaume Jochen Scholl
  • Patent number: 10619496
    Abstract: A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, John T. Ols
  • Patent number: 10612563
    Abstract: An air conditioner comprises a compressor to compress a refrigerant, a heat exchanger to move heat of the refrigerant, and a blower to blow air. The blower comprises a fan rotatable about a rotation axis, and a plurality of stationary blades installed to be a radial shape about the rotation axis in a direction in which the airflow generated by the rotation of the fan is discharged, and are curved in a direction opposite to the rotation direction of the fan from an inner circumferential portion to an outer circumferential portion. The stationary blades comprise an inlet edge, and an outlet edge, and an inlet angle formed by the inlet edge and the rotation axis and a chord angle formed by a chord connecting the inlet edge and the outlet edge and the rotation axis are larger at the inner and outer circumferential portions than at a radial center portion.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: April 7, 2020
    Assignee: SAMSUNG ELECTRONICS CO., LTD.
    Inventor: Seiji Sato
  • Patent number: 10590782
    Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: March 17, 2020
    Assignee: CHROMALLOY GAS TURBINE LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
  • Patent number: 10590954
    Abstract: The invention relates to a flow-conducting grille designed as a pre-conducting grille for arranging on a suction region of a fan, wherein the flow-conducting grille has a grille web structure about an axial center line, which grille web structure comprises radial webs spaced apart in the circumferential direction and coaxial circumferential webs spaced apart in the radial direction and an outer ring, wherein an inflow side of the flow-conducting grille extends flat and parallel to a radial plane of the flow-conducting grille.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: March 17, 2020
    Assignee: ebm-papst Mulfingen GmbH & Co. KG
    Inventors: Zhang Binyuan, Christian Haag, Carsten Hübner, Björn Sudler, Manuel Vogel
  • Patent number: 10583932
    Abstract: A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is: the ? ? turbine ? ? diameter ? ? at ? ? an ? ? axial location ? ? of ? ? the ? ? lowest ? ? pressure ? ? rotor ? ? stage ? ground ? ? plane ? ? to ? ? wing ? ? distance and a quasi-non-dimensional mass flow rate Q defined as: Q = W ? T ? ? 0 P ? ? 0 · A flow where: W is mass flow rate through the fan in Kg/s; T0 is average stagnation temperature of the air at the fan face in Kelvin; P0 is average stagnation pressure of the air at the fan face in Pa; and Aflow is the flow area of the fan face in m2, and wherein a Q ratio of: the downstream blockage ratio×Q is in a range from 0.005 to 0.01.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: March 10, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard G Stretton, Michael C Willmot
  • Patent number: 10577937
    Abstract: A fan blade is provided with an aerofoil portion for which, for cross-sections through the aerofoil portion at radii between 15% and 25% of the blade span from the root radius, the average leading edge thickness is greater than the leading edge thickness at the tip. The geometry of the fan blade may result in a lower susceptibility to flutter.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: March 3, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Mark J. Wilson, Gabriel Gonzalez-Gutierrez, Marco Barale, Benedict Phelps, Kashmir S. Johal, Nigel H S Smith
  • Patent number: 10577953
    Abstract: A stator vane is comprised of: an airfoil section elongated in a radial direction relative to an axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout these sections and unitized with a ceramic.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: March 3, 2020
    Assignee: IHI Corporation
    Inventor: Fumiaki Watanabe
  • Patent number: 10577938
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: March 3, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Julien Mervant, Vincent Nicolas Leonardon, Pierre Hervé Fernand Marche, Pascal Pierre Nicolas Routier, Ludovic Pintat
  • Patent number: 10570767
    Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: February 25, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Russell Ratzlaff, Ronald Scott Bunker
  • Patent number: 10563669
    Abstract: A fan includes an impeller including a boss that is a rotation center, and a plurality of blades that are provided on an outer peripheral surface of the boss; a motor and a motor fixing portion rotationally driving the impeller; a housing accommodating the impeller; a plurality of stationary blades disposed downstream of the impeller and connecting the motor fixing and the housing; and a connecting portion disposed between the housing and a rotation axis of the impeller, and extending in a rotation direction of the impeller and connecting the plurality of stationary blades. The connecting portion has a recessed portion for passing wind that flows in a radial direction of the impeller.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: February 18, 2020
    Assignee: Mitsubishi Electric Corporation
    Inventors: Kenichi Sakoda, Tomoya Fukui, Masayuki Oishi
  • Patent number: 10533452
    Abstract: An acoustic damper includes a housing with an inlet aperture and an outlet aperture. The housing is configured to receive a gas flow that enters via the inlet aperture and that exits via the outlet aperture. The acoustic damper also includes a barrier member that is disposed within the housing. The barrier member is configured to be disposed within the gas flow and to dampen acoustic energy that propagates in an upstream direction generally from the outlet aperture toward the inlet aperture. The barrier member includes an outer structure that defines an interior volume of the barrier member. The interior volume is oriented toward the outlet aperture.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: January 14, 2020
    Assignee: GARRETT TRANSPORTATION I INC.
    Inventors: Bhushan Singh Gautam, Gladys Gaude
  • Patent number: 10526895
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: January 7, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Vincent Nicolas Leonardon, Thomas Michel Julien Mervant, Guillaume Jochen Scholl, Ludovic Pintat, Renaud Gabriel Constant Royan
  • Patent number: 10508550
    Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: December 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Loubriel Ramirez
  • Patent number: 10508559
    Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.
    Type: Grant
    Filed: November 12, 2013
    Date of Patent: December 17, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Matthieu Gimat, Dominique Marie Christian Coupe
  • Patent number: 10480531
    Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: November 19, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Takanori Shibata, Naoto Omura, Chihiro Myoren, Yasuo Takahashi
  • Patent number: 10465559
    Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ky H. Vu, Bryan P. Dube, Michael J. Allen
  • Patent number: 10458245
    Abstract: When cold and in the non-coated state, a turbine blade includes an aerodynamic profile that is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Pierre Routier, Vincent Nicolas Leonardon, Daniel Marius Man, Pierre Hervé Marche
  • Patent number: 10458246
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 29, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Mervant, Erwan Daniel Botrel, Maxime Didier Delabriere, Jean-Armand Marc Destouches
  • Patent number: 10415406
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: September 17, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Neil Ristau, Russell DeForest, Frederic Woodrow Roberts, Jr.
  • Patent number: 10408227
    Abstract: The present disclosure is directed toward airfoils used in gas turbine engines. More specifically, the present disclosure teaches airfoils with fillets for managing stresses in airfoils during use in gas turbine engines.
    Type: Grant
    Filed: July 13, 2016
    Date of Patent: September 10, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Patrick E. Bailey, Timothy Unton
  • Patent number: 10352330
    Abstract: A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.
    Type: Grant
    Filed: October 10, 2014
    Date of Patent: July 16, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Damien Joseph Cellier
  • Patent number: 10329914
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: June 25, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Marius Man, Maxime Didier Delabriere, Pierre Hervé Marche, Pascal Pierre Routier
  • Patent number: 10309419
    Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
    Type: Grant
    Filed: October 11, 2012
    Date of Patent: June 4, 2019
    Assignee: SAFRAN AIRCARFT ENGINES
    Inventors: Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
  • Patent number: 10301944
    Abstract: A cast turbine blade having a platform and hollow blade airfoil arranged thereon, wherein the blade airfoil has a pressure-side blade wall and a suction-side blade wall that extend, along a centrally arranged curved profile centerline, from a common leading edge to a common trailing edge, and having a transition, with an outer contour profile, between the blade airfoil and the platform. The blade walls each have a locally determined blade wall thickness, wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition such that the region of the transition has an essentially constant blade wall thickness. In the transition, the contour profile at a surface section of the blade airfoil facing the leading edge is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: May 28, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Björn Buchholz, Ralph Gossilin, Daniela Koch, Marco Schüler
  • Patent number: 10294796
    Abstract: A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span. Each aerofoil has pressure side, a suction side, a leading edge region and a leading edge foot extending from the leading edge region, the leading edge foot has a ridge line. The platform defines a channel and a platform leading edge, the channel has a minimum radial height line, and the platform leading edge partly defines an outlet through which a secondary flow passes. The ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow.
    Type: Grant
    Filed: July 29, 2014
    Date of Patent: May 21, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Yan Sheng Li, Roy Teuber
  • Patent number: 10288086
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, John David Dyer
  • Patent number: 10287889
    Abstract: A power turbine includes a first stage vane having an airfoil with a cold nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: May 14, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Niloofar Moradi
  • Patent number: 10280777
    Abstract: A method and system including a circumferential seal assembly for sealing between components within a turbine is provided. A circumferential seal assembly is disposed in a slot extending circumferentially about an inner barrel. The seal assembly includes a first shim layer and at least one additional shim layer configured in an overlapping stacked configuration so as to stagger the end portions of each of the shim segments defined by the shim layers, relative to one another and circumferentially about the seal assembly. One or more cloth layers are configured wrapping about the first shim layer and the at least one additional shim layer to define a sealing member having a first sealing surface and a second sealing surface. The assembly further including a base plate, wherein the sealing member is disposed on an upper surface of the base plate to provide for sealing engagement between the components of the turbine.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: May 7, 2019
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Norman Arnold Turnquist, Christopher Edward Wolfe
  • Patent number: 10280774
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: May 7, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: John Franklin Ryman, Victor John Morgan, Mary Virginia Holloway